EP2485941A2 - Pressure fuselage of an aircraft comprising a tail-face pressure calotte - Google Patents

Pressure fuselage of an aircraft comprising a tail-face pressure calotte

Info

Publication number
EP2485941A2
EP2485941A2 EP10762689A EP10762689A EP2485941A2 EP 2485941 A2 EP2485941 A2 EP 2485941A2 EP 10762689 A EP10762689 A EP 10762689A EP 10762689 A EP10762689 A EP 10762689A EP 2485941 A2 EP2485941 A2 EP 2485941A2
Authority
EP
European Patent Office
Prior art keywords
pressure
section
fuselage
aircraft
profile
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP10762689A
Other languages
German (de)
French (fr)
Other versions
EP2485941B1 (en
Inventor
Cihangir Sayilgan
Martin Beckmann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Publication of EP2485941A2 publication Critical patent/EP2485941A2/en
Application granted granted Critical
Publication of EP2485941B1 publication Critical patent/EP2485941B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/10—Bulkheads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections

Definitions

  • the present invention relates to a pressure hull of an aircraft, which in
  • Hull of the latter aircraft forms the force-bearing structure.
  • longitudinal forces and perpendicular to the longitudinal direction torsional forces are inter alia initiated by the wings, the engines and the tail.
  • the high mechanical stiffness of the outer shell relative to the forces acting results due to the substantially tubular elongated structure of the hull.
  • longitudinal stringers in combination with circumferentially extending annular ribs provide the required stability of the hull.
  • the Stringer and LK: hv Spans prevent buckling or the like from forming in the outer shell, which could reduce the mechanical load-bearing capacity of the outer shell with respect to longitudinal, lateral and torsional forces.
  • the fuselage has an aircraft interior under atmospheric pressure
  • the cargo hold of an aircraft is also under atmospheric pressure. Outside the aircraft interior pressure range primarily units and the like are arranged.
  • a hull of this type is referred to in the context of the present invention as a pressure hull.
  • the pressure hull can be composed of several fuselage sections, which is used as an alternative to or in addition to a shell division especially in the construction of very long hulls.
  • the present invention relates to hulls after the
  • Hull structure has an annular main segment which has a cross-sectional opening which is closed by a pressure dome.
  • tie rods connect the pressure cap with the annular main segment and take on the
  • Pressure dome requires from both sides. Because from one side of the rivet must be beaten and on the opposite side of this must be countered. Due to the geometry, it is not possible in practice to squeeze rivets. In addition, the accessibility on the side of the rear area is very high because of the small accessible height unfavorable. Therefore, the pressure cap is usually mounted in a fairly early assembly step of the aircraft. For this reason, pre-equipment with systems is only possible to a limited extent at best. Furthermore fall when drilling the rivet holes on both sides of the
  • the object of the present invention to provide a pressure hull of an aircraft, the pressure dome can be installed easily with a few connection and support elements.
  • the invention includes the technical teaching that provided for fastening the pressure cap special Spantprofil druckkalotten note has a U-shaped profile section, the end side of the first leg via connecting means back to the
  • Pressure dome is attached and its extended radially outwardly extending second leg so connects to at least one fuselage section manufactures that the connecting means are mountable alone from the aircraft interior pressure range ago.
  • the advantage of the solution according to the invention is, in particular, that because of the function-integrated special bulkhead profile, fewer individual components are required in order to carry out a pressure cap fastening. This reduces accordingly the number of individual connection points.
  • the solution according to the invention leads to a reduced workload.
  • the only one-sided accessibility namely, from the aircraft interior pressure range forth, causes assembly staff not on both sides of the pressure dome must be available to produce the preferably designed as riveting joints between Spantprofil and Druckkalotte. Due to the one-sided mounting position, it is possible to squeeze the rivet instead of just shooting it.
  • the solution according to the invention also provides the prerequisite for carrying out a subsequent installation during the production process of the aircraft and thus to enable a preliminary equipment of the pressure bulkhead with systems.
  • a plurality of spaced apart along the circumferential circle of the pressure dome arranged tension struts are provided, which are attached to the one end via the connecting means at the edge of the pressure dome, and with the other end to the adjacent pressure range side fuselage section.
  • the tension struts are loaded only on train and prevent bending of the bulkhead profile according to the invention as a result of the pressure difference between the aircraft interior pressure area and the standing during the flight at a lower pressure outside area.
  • the required static stability of the construction in the critical outer radial edge region of the pressure is guaranteed.
  • each tie rod is formed as a sufficiently tensile metal strip, which is provided at both end regions with openings for receiving connecting means, preferably rivets.
  • connecting means preferably rivets.
  • Support function can be realized by a fairly lightweight constructive design.
  • the extended radially outwardly extending second leg of the bulkhead opens according to another, improving the invention measure in a T-shaped
  • Fuselage section takes place. Also suitable for this are rivets on both sides of the
  • two adjacent fuselage sections can be interconnected by the cross section of the T-shaped profile section. It thus eliminates an otherwise required gap bridging frame.
  • Passenger cabin matching pressure range be constructed of longitudinally split shell halves.
  • the Spantprofil invention has part of the
  • the hull is configured as a so-called wound hull
  • the frame profile is made in one piece, thus forming a full ring of 360 °.
  • the frame profile should be as light as possible.
  • the frame profile composed of the U-shaped and the T-shaped profile section is manufactured as a milling component consisting of light metal.
  • a light metal for example, titanium or a titanium alloy can be used to ensure a sufficient material strength.
  • FIG. 1 is a schematic side view of an aircraft with pressure hull, which is composed of several fuselage sections without shell division,
  • FIG. 2 is a schematic side view of an aircraft with pressure hull, which is composed of several fuselage sections with shell division,
  • FIG. 4 shows a schematic partial enlargement in the region of the connection point between the pressure cap and adjacent fuselage sections from FIG.
  • the pressure hull of the aircraft seen in the longitudinal direction of several fuselage sections la-le, which are connected at the boundary points over closed oval ring cross-sections with each other to produce a long-building pressure hull.
  • a rear-side pressure calotte 2 is provided via a special frame profile 5 attached, which has an aircraft-internal printing area 3 of a non-printed
  • Rear section separates, which is assigned to the fuselage section lf.
  • the passenger cabin Within the aircraft-internal pressure range 3 are the passenger cabin and one below it
  • FIG. 2 schematically illustrates a pressure hull which is constructed according to the so-called shell division concept.
  • the outer shell of the pressure hull surrounding the aircraft interior pressure region 3 is formed in two parts.
  • this area consists of an upper half-shell 4a and a lower half-shell 4b. Both half-shells 4a and 4b terminate at the rear on the pressure cap 2, so that the two half-shells 4a and 4b adjoin the bulkhead 2, which secures the pressure cap 2 relative to the pressure hull, on the part of the airplane-internal pressure area 3.
  • Connecting means 7 is secured rearwardly on the pressure cap 2.
  • the extended radially outwardly extending second leg 7 of the U-shaped profile section connects to the two fuselage sections le and lf.
  • tie rods 10 are provided in addition to this several spaced apart along the circumferential circle of the pressure cap 5 arranged tie rods 10. Also, the individual tie rods 10 are attached to the one end via the connecting means 7 on the pressure cap 2 and analogous to the other end also on the associated pressure range side fuselage section le.
  • Longitudinal stringer 11 form on both sides of the bulkhead profile 5 arranged
  • Stringerkupp treatment parts 12a and 12b a static node.
  • the layer structure in the region of the node results from the outside to the inside in such a way that on the outer shell 13 of the adjacent fuselage section le and lf inside a Spaltabdichtungsband 14 is applied, whereupon the cross piece 9 of the T-shaped
  • Profile section of the rib profile 5 is applied gap bridging.
  • the two Stringerkupp treatment parts 12a and 12b as a kind of clamping jaws. All the above components are firmly connected by - not shown - rivets.

Abstract

The invention relates to a pressure fuselage of an aircraft, said pressure fuselage being composed of several fuselage sections (1a-1f) in the longitudinal direction, wherein at least one tail-face pressure calotte (2) is provided for forming an inner pressurized area (3) of the aircraft. An annular frame section (5) is provided in order to fix said pressure calotte radially outward to at least one fuselage section (1a-1f). The frame section (5) has a U-shaped section segment on the pressure calotte side. The first arm (6) of the section segment on the end face thereof is rearwardly fixed to the pressure calotte (2) by connecting means (7), and the elongated second arm (8) of the section segment, said second arm extending radially outward, produces a connection to at least one fuselage section (1e, 1f) such that the connecting means (7) can be mounted entirely from the inner pressurized area of the aircraft.

Description

Druckrumpf eines Flugzeuges mit heckseitiger Druckkalotte  Pressure hull of an airplane with rear-side pressure calotte
GEBIET DER ERFINDUNG FIELD OF THE INVENTION
Die vorliegende Erfindung betrifft einen Druckrumpf eines Flugzeuges, welcher in The present invention relates to a pressure hull of an aircraft, which in
Längsrichtung aus mehreren Rumpfsektionen zusammengesetzt ist, wobei mindestens eine heckseitige Druckkalotte zur Bildung eines flugzeuginneren Druckbereichs vorgesehen ist, zu deren außenradialer Befestigung an mindestens einer Rumpfsektion ein ringförmiges Longitudinally composed of a plurality of fuselage sections, wherein at least one rear-side pressure calotte is provided for forming an aircraft-internal pressure area, to the outer radial attachment to at least one fuselage section an annular
Spantprofil vorgesehen ist. Frame profile is provided.
Das Einsatzgebiet der vorliegenden Erfindung erstreckt sich vornehmlich auf die The field of application of the present invention extends primarily to the
Verkehrsflugzeugtechnik. Zum Transport von Personen oder Gütern kommen gewöhnlich Transport aircraft technology. To transport people or goods usually come
Verkehrsflugzeuge mit einem großvolumigen Rumpf zum Einsatz, der in mehrere Ebenen aufgeteilt sein kann. So existieren neben gewickelten Rumpfkonstruktionen auch Commercial aircraft with a large-volume hull is used, which can be divided into several levels. Thus, besides wound hull constructions also exist
Rumpfkonstruktionen, die dem so genannten Schalenteilungskonzept zuzuordnen sind. Der Hull constructions, which are assigned to the so-called shell division concept. Of the
Rumpf letztgenannter Flugzeuge bildet die krafttragende Struktur. In Rumpfschalen werden längswirkende Kräfte und senkrecht zur Längsrichtung wirkende Torsionskräfte unter anderem von den Tragflächen, den Triebwerken und dem Leitwerk eingeleitet. Die hohe mechanische Steifigkeit der Außenschale gegenüber den wirkenden Kräften ergibt sich aufgrund des im Wesentlichen rohrförmig langgestreckten Aufbaus des Rumpfes. Innerhalb des Schalenaufbaus sorgen längsverlaufende Stringer in Kombination mit in Umfangsrichtung verlaufende ringartige Spante für die erforderliche Stabilität des Rumpfes. Die Stringer und LK:hv Spante verhindern, dass sich in der Außenschale Beulen oder dergleichen bilden können, welche die mechanische Tragfähigkeit der Außenschale gegenüber Längs-, Quer- und Torsionskräften verringern könnte. Hull of the latter aircraft forms the force-bearing structure. In torso shells longitudinal forces and perpendicular to the longitudinal direction torsional forces are inter alia initiated by the wings, the engines and the tail. The high mechanical stiffness of the outer shell relative to the forces acting results due to the substantially tubular elongated structure of the hull. Within the shell structure, longitudinal stringers in combination with circumferentially extending annular ribs provide the required stability of the hull. The Stringer and LK: hv Spans prevent buckling or the like from forming in the outer shell, which could reduce the mechanical load-bearing capacity of the outer shell with respect to longitudinal, lateral and torsional forces.
Für den Transport von Gütern und insbesondere Personen in großen Flughöhen ist es erforderlich, dass der Atmosphärendruck innerhalb des Rumpfes in etwa erhalten bleibt. Hierfür weist der Rumpf einen unter Atmosphärendruck stehenden flugzeuginneren For the transport of goods and in particular persons at high altitudes, it is necessary that the atmospheric pressure within the hull be maintained approximately. For this purpose, the fuselage has an aircraft interior under atmospheric pressure
Druckbereich auf. In der Regel steht neben einer Passagierkabine auch der Frachtraum eines Flugzeugs unter Atmosphärendruck. Außerhalb des flugzeuginneren Druckbereichs werden vornehmlich Aggregate und dergleichen angeordnet. Ein Rumpf dieser Art wird im Rahmen der vorliegenden Erfindung als Druckrumpf bezeichnet. Print area on. As a rule, besides a passenger cabin, the cargo hold of an aircraft is also under atmospheric pressure. Outside the aircraft interior pressure range primarily units and the like are arranged. A hull of this type is referred to in the context of the present invention as a pressure hull.
Der Druckrumpf kann aus mehreren Rumpfsektionen zusammengesetzt sein, der alternativ zu oder auch neben einer Schalenteilung insbesondere bei der Konstruktion sehr langbauender Rümpfe verwendet wird. Die vorliegende Erfindung lässt sich auf Rümpfe nach dem The pressure hull can be composed of several fuselage sections, which is used as an alternative to or in addition to a shell division especially in the construction of very long hulls. The present invention relates to hulls after the
Schalenteilungskonzept mit gleichzeitiger oder alternativer Sektionsteilung anwenden. Apply shell sharing concept with simultaneous or alternative section division.
Aus der DE 10 2006 027 707 AI geht ein Druckrumpf eines gattungsgemäßen Flugzeuges hervor. Im Heckbereich des Druckrumpfes geht der flugzeuginnere Druckbereich - die Kabine - in einen heckseitigen nicht unter Druck stehenden Bereich über. In diesem Bereich wird die tragende Außenschale durch innenliegende längsverlaufende Stringer und quer dazu angeordnete Spanten gestützt. Die Spanten weisen eine Form entsprechend dem Querschnitt der Außenschale auf, die im Wesentlichen ringförmig ist. Das Tragwerk, welches durch die Stringer und die Spanten gebildet wird, besitzt selbst keine oder nur geringe mechanische Tragfähigkeit. Die Tragfähigkeit wirkt in dieser Rumpfsektion erst in Verbindung mit der Außenschale. Aufgrund des Druckunterschiedes zwischen dem Druckrumpf und dem nicht unter Druck stehenden Heckbereich wirken Kräfte in Längsrichtung auf ein die Grenze bildendes Druckschott. Damit das Druckschott eine ausreichende mechanische Stabilität gegenüber diesen Kräften erhält, sind diverse Verstrebungen vorhanden. Zusätzlich wird eine nach außen in Richtung des nicht unter Druck stehenden Heckbereichs gewölbte Druckkalotte in das Druckschott integriert. Die Verbindung zwischen dem außenradialen Randbereich der gewölbten Druckkalotte mit dem angrenzenden Spant muss druckdicht und entsprechend den herrschenden Beanspruchungen stabil ausgeführt sein. Nachteilhaft bei dieser Lösung des Standes der Technik erscheint die recht aufwendige Verbindung mit diversen Verstrebungen und der hierdurch verursachte erhebliche Montageaufwand. From DE 10 2006 027 707 Al a pressure hull of a generic aircraft emerges. In the rear area of the pressure hull, the aircraft-internal pressure area - the cabin - changes into a non-pressurized rear area. In this area, the supporting outer shell is supported by inner longitudinal stringer and transverse thereto arranged frames. The frames have a shape corresponding to the cross section of the outer shell, which is substantially annular. The structure, which is formed by the stringers and the frames, has no or little mechanical load capacity itself. The load capacity in this fuselage section only works in conjunction with the outer shell. Due to the pressure difference between the pressure hull and the non-pressurized rear area forces act in the longitudinal direction of a forming the limit pressure bulkhead. Thus, the pressure bulkhead sufficient mechanical stability receives against these forces, various bracing are available. In addition, a curved outward in the direction of the non-pressurized rear area pressure dome is integrated into the pressure bulkhead. The connection between the outer radial edge region of the curved pressure dome with the adjacent bulkhead must be pressure-tight and made stable according to the prevailing stresses. A disadvantage of this solution of the prior art, the quite complex connection with various braces and the resulting considerable installation effort.
Aus der DE 10 2007 052 140 AI geht eine andere technische Lösung für die Befestigung einer Druckkalotte innerhalb eines Druckrumpfes eines Flugzeuges hervor. Die From DE 10 2007 052 140 AI another technical solution for the attachment of a pressure dome within a pressure hull of an aircraft emerges. The
Rumpfstruktur weist ein ringförmiges Hauptsegment auf, welches eine Querschnittsöffnung besitzt, die über eine Druckkalotte verschlossen ist. Mehrere Zugstreben verbinden die Druckkalotte mit dem ringförmigen Hauptsegment und nehmen dabei die auf die Hull structure has an annular main segment which has a cross-sectional opening which is closed by a pressure dome. Several tie rods connect the pressure cap with the annular main segment and take on the
Druckkalotte wirkenden Lasten als Zuglasten auf. Durch diese technischen Lösungen können biegebeanspruchte Verstärkungselemente vermieden werden. Hierdurch lassen sich die Zugstreben auch mit einem kleineren Querschnitt ausbilden, woraus sich eine Druckkalotte acting loads as tensile loads on. By means of these technical solutions, bending-stressed reinforcing elements can be avoided. As a result, the tie rods can be formed with a smaller cross-section, resulting in a
Gewichtseinsparung ergibt. Weight saving results.
Allerdings sind für die druckdichte Verbindung der Druckkalotte mit der benachbarten Rumpfsektion weitere Bauteile erforderlich, insbesondere gebogene Ringspante mit speziellen Biegeradien, die über Abstützwinkel stabil an der Rumpfsektion zu befestigen sind. Die insgesamt recht vielen einzelnen Verbindungs- und Stützelemente sind daher sehr aufwendig zu montieren. Insbesondere beim Vernieten der Druckkalotte mit den However, further components are required for the pressure-tight connection of the pressure calotte with the adjacent fuselage section, in particular curved ring frame with special bending radii, which are to be fixed stably to the fuselage section via support angles. The total number of individual connection and support elements are therefore very expensive to assemble. Especially when riveting the pressure cap with the
zugeordneten Stützelementen sind Nieten zu setzen, welche eine Zugänglichkeit der associated support elements are rivets to set, which provides accessibility of the
Druckkalotte von beiden Seiten her erfordert. Denn von einer Seite muss der Niet geschlagen werden und auf der gegenüberliegenden Seite muss dieser gegengehalten werden. Aufgrund der Geometrie ist es in der Praxis nicht möglich, Niete zu quetschen. Außerdem ist die Zugänglichkeit auf der Seite des Heckbereichs wegen der geringen begehbaren Höhe sehr ungünstig. Daher wird die Druckkalotte gewöhnlich in einem recht früheren Montageschritt des Flugzeuges montiert. Eine Vorausrüstung mit Systemen ist aus diesem Grunde bestenfalls nur eingeschränkt möglich. Ferner fallen beim Bohren der Nietlöcher beidseits der Pressure dome requires from both sides. Because from one side of the rivet must be beaten and on the opposite side of this must be countered. Due to the geometry, it is not possible in practice to squeeze rivets. In addition, the accessibility on the side of the rear area is very high because of the small accessible height unfavorable. Therefore, the pressure cap is usually mounted in a fairly early assembly step of the aircraft. For this reason, pre-equipment with systems is only possible to a limited extent at best. Furthermore fall when drilling the rivet holes on both sides of the
Druckkalotte Späne an, welche recht aufwendig zu entfernen sind. Druckkalotte chips, which are quite expensive to remove.
HINTERGRUND DER ERFINDUNG BACKGROUND OF THE INVENTION
Es ist daher die Aufgabe der vorliegenden Erfindung, einen Druckrumpf eines Flugzeuges zu schaffen, dessen Druckkalotte sich auf einfache Weise mit wenigen Verbindungs- und Stützelementen installieren lässt. It is therefore the object of the present invention to provide a pressure hull of an aircraft, the pressure dome can be installed easily with a few connection and support elements.
Die Aufgabe wird ausgehend von einem Druckrumpf gemäß dem Oberbegriff von Anspruch 1 in Verbindung mit dessen kennzeichnenden Merkmalen gelöst. Die nachfolgenden abhängigen Ansprüche geben vorteilhafte Weiterbildungen der Erfindung wieder. The object is achieved on the basis of a pressure hull according to the preamble of claim 1 in conjunction with its characterizing features. The following dependent claims give advantageous developments of the invention.
Die Erfindung schließt die technische Lehre ein, dass das zur Befestigung der Druckkalotte vorgesehene spezielle Spantprofil druckkalottenseitig einen U-förmigen Profilabschnitt aufweist, dessen endseitig erster Schenkel über Verbindungsmittel rückwärtig an der The invention includes the technical teaching that provided for fastening the pressure cap special Spantprofil druckkalottenseitig has a U-shaped profile section, the end side of the first leg via connecting means back to the
Druckkalotte befestigt ist und dessen verlängerter sich nach radial außen erstreckender zweiter Schenkel derart eine Verbindung zur mindestens einen Rumpfsektion herstellt, dass die Verbindungsmittel allein vom flugzeuginneren Druckbereich her montierbar sind. Pressure dome is attached and its extended radially outwardly extending second leg so connects to at least one fuselage section manufactures that the connecting means are mountable alone from the aircraft interior pressure range ago.
Der Vorteil der erfindungsgemäßen Lösung liegt insbesondere darin, dass wegen des funktionsintegrierten speziellen Spantprofils weniger einzelne Bauelemente erforderlich sind, um eine Druckkalottenbefestigung vorzunehmen. Damit reduziert sich entsprechend auch die Anzahl der einzelnen Verbindungsstellen. Insgesamt führt die erfindungsgemäße Lösung zu einem reduzierten Arbeitsaufwand. Insbesondere die nur noch einseitige Zugänglichkeit, nämlich vom flugzeuginneren Druckbereich her, führt dazu, dass Montagepersonal nicht beidseits der Druckkalotte zur Verfügung stehen muss, um die vorzugsweise als Nietstellen ausgeführten Verbindungsstellen zwischen Spantprofil und Druckkalotte zur erzeugen. Bedingt durch die einseitige Montageposition besteht die Möglichkeit, die Niete zu quetschen, anstatt sie lediglich zu schießen. Die erfindungsgemäße Lösung bietet darüber hinaus die Voraussetzung dafür, eine spätere Installation während des Produktionsprozesses des Flugzeuges durchzuführen und somit eine Vorausrüstung des Druckschotts mit Systemen zu ermöglichen. The advantage of the solution according to the invention is, in particular, that because of the function-integrated special bulkhead profile, fewer individual components are required in order to carry out a pressure cap fastening. This reduces accordingly the number of individual connection points. Overall, the solution according to the invention leads to a reduced workload. In particular, the only one-sided accessibility, namely, from the aircraft interior pressure range forth, causes assembly staff not on both sides of the pressure dome must be available to produce the preferably designed as riveting joints between Spantprofil and Druckkalotte. Due to the one-sided mounting position, it is possible to squeeze the rivet instead of just shooting it. The solution according to the invention also provides the prerequisite for carrying out a subsequent installation during the production process of the aircraft and thus to enable a preliminary equipment of the pressure bulkhead with systems.
Mit anderen Worten wird die Druckkalotte also direkt am erfindungsgemäßen In other words, the pressure cap is thus directly on the invention
funktionsintegrierten Spantprofil befestigt. Ein zusätzliches Übergangsstück und zugehörige Verbindungsmittel können insoweit entfallen. attached functionally integrated frame profile. An additional transition piece and associated connection means can be omitted in this respect.
Gemäß einer die Erfindung verbessernden Maßnahme sind mehrere beabstandet zueinander entlang des Umfangskreises der Druckkalotte angeordnete Zugstreben vorgesehen, welche mit dem einen Ende über die Verbindungsmittel am Rand der Druckkalotte, und die mit dem anderen Ende an der benachbarten druckbereichsseitigen Rumpfsektion angebracht sind. Entsprechend ihrer technischen Funktion sind die Zugstreben lediglich auf Zug belastet und verhindern ein Verbiegen des erfindungsgemäßen Spantprofils in Folge der Druckdifferenz zwischen dem flugzeuginneren Druckbereich und dem während des Fluges unter einem geringeren Druck stehenden Außenbereich. Hierdurch wird die erforderliche statische Stabilität der Konstruktion im kritischen außenradialen Randbereich der Druckkalotte garantiert. According to a measure improving the invention, a plurality of spaced apart along the circumferential circle of the pressure dome arranged tension struts are provided, which are attached to the one end via the connecting means at the edge of the pressure dome, and with the other end to the adjacent pressure range side fuselage section. According to their technical function, the tension struts are loaded only on train and prevent bending of the bulkhead profile according to the invention as a result of the pressure difference between the aircraft interior pressure area and the standing during the flight at a lower pressure outside area. As a result, the required static stability of the construction in the critical outer radial edge region of the pressure is guaranteed.
Vorzugsweise ist jede Zugstrebe als ein hinreichend zugfestes Metallband ausgebildet, welches an beiden Endbereichen mit Durchbrüchen zur Aufnahme von Verbindungsmitteln, vorzugsweise Niete, versehen ist. Hierdurch kann die durch die Zugstrebe bewirkte Preferably, each tie rod is formed as a sufficiently tensile metal strip, which is provided at both end regions with openings for receiving connecting means, preferably rivets. As a result, caused by the tension strut
Stützfunktion durch eine recht leichtbauende konstruktive Ausführung realisiert werden. Der verlängerte sich nach radial außen erstreckende zweite Schenkel des Spantprofils mündet gemäß einer weiteren, die Erfindung verbessernden Maßnahme in einen T-förmigen Support function can be realized by a fairly lightweight constructive design. The extended radially outwardly extending second leg of the bulkhead opens according to another, improving the invention measure in a T-shaped
Profilabschnitt, über dessen Querstück die Befestigung an der mindestens einen Profile section, on whose cross piece the attachment to the at least one
Rumpfsektion erfolgt. Auch hierfür eignen sich wiederum Niete, die beidseits des Fuselage section takes place. Also suitable for this are rivets on both sides of the
verlängerten Schenkels zu beiden Enden des Querstücks anzubringen sind. Somit sind keine weiteren Profilteile oder dergleichen Konstruktionshilfselemente erforderlich, um das erfindungsgemäße Spantprofil an der zugeordneten Rumpfsektion zu befestigen. extended leg are to be attached to both ends of the crosspiece. Thus, no further profile parts or the like auxiliary construction elements are required in order to fasten the frame profile according to the invention to the associated fuselage section.
Vorteilhafterweise können durch den Querschnitt des T-förmigen Profilabschnitts zwei benachbarte Rumpfsektionen miteinander verbunden werden. Es entfällt insoweit ein ansonsten erforderlicher spaltüberbrückender Spant. Advantageously, two adjacent fuselage sections can be interconnected by the cross section of the T-shaped profile section. It thus eliminates an otherwise required gap bridging frame.
Die erfindungsgemäße Lösung lässt sich in Bezug auf verschiedene The solution according to the invention can be compared with respect to various
Rumpf konstruktionskonzepte umsetzen. So kann der Rumpf in dem in etwa mit der Implement hull design concepts. So the hull in the roughly with the
Passagierkabine übereinstimmenden Druckbereich aus längsgeteilten Schalenhälften aufgebaut sein. In diesem Falle hat das erfindungsgemäße Spantprofil seitens des Passenger cabin matching pressure range be constructed of longitudinally split shell halves. In this case, the Spantprofil invention has part of the
Druckbereichs zwei Schalenhälften von je 180° zu verbinden, wogegen die heckseitige Rumpfsektion gewöhnlich einen vollen Ring von 360° an der Verbindungsstelle bildet. Zur Abstimmung hierauf wird gemäß einer anderen, die Erfindung verbessernden Maßnahme vorgeschlagen, dass das erfindungsgemäße Spantprofil geteilt ausgeführt ist, wobei jedes Spantprofilteil ein Ringsegment von bis zu 180° bildet. Pressure range two shell halves of 180 ° to connect, whereas the rear fuselage section usually forms a full ring of 360 ° at the junction. To vote on this, according to another measure improving the invention, it is proposed that the frame profile according to the invention be made split, wherein each frame profile part forms a ring segment of up to 180 °.
Sollte der Rumpf dagegen als ein so genannter gewickelter Rumpf ausgeführt sein, so liegt an der Verbindungsstelle zum erfindungsgemäßen Spantprofil genau so wie seitens der heckseitigen Rumpfsektion ein durchgängiger Ring an. In Anpassung hierauf wird vorgeschlagen, dass das Spantprofil einteilig ausgeführt ist, und somit einen vollen Ring von 360° bildet. Wie generell im Flugzeugbau angestrebt, sollte das Spantprofil möglichst leichtbauend sein. Um dieses Ziel zu erreichen, wird vorgeschlagen, dass das aus dem U- förmigen und dem T- förmigen Profilabschnitt zusammengesetzte Spantprofil als ein aus Leichtmetall bestehendes Fräsbauteil gefertigt ist. Als Leichtmetall kann beispielsweise Titan oder eine Titanlegierung verwendet werden, um eine hinreichende Materialfestigkeit sicherzustellen. Anstatt der fertigungstechnischen Ausführung durch Fräsen ist es auch denkbar, das Spantprofil gießtechnisch herzustellen. Nach dem Gießen ist in der Regel eine zumindest teilweise spanende Bearbeitung erforderlich. If, on the other hand, the hull is configured as a so-called wound hull, then at the connection point to the frame profile according to the invention, there is a continuous ring just as on the stern-side fuselage section. In adaptation to this it is proposed that the frame profile is made in one piece, thus forming a full ring of 360 °. As generally desired in aircraft construction, the frame profile should be as light as possible. In order to achieve this goal, it is proposed that the frame profile composed of the U-shaped and the T-shaped profile section is manufactured as a milling component consisting of light metal. As a light metal, for example, titanium or a titanium alloy can be used to ensure a sufficient material strength. Instead of the production engineering design by milling, it is also conceivable to produce the frame profile by casting. After casting, at least partial machining is usually required.
Zur Bildung der statischen Knotenpunkte zwischen dem erfindungsgemäßen Spantprofil und hierzu längsverlaufenden Stringern wird vorgeschlagen, beidseitig des Spantprofils angeordnete spezielle Stringerkupplungsteile zu verwenden. Die Stringerkupplungsteile sind in ihrer Form an die miteinander zu verbindenden Teile im Bereich des statischen To form the static nodes between the Spantprofil invention and this longitudinally extending stringers is proposed to use both sides of the Spantprofils special string coupling parts. The stringer coupling parts are in their shape to the parts to be joined together in the static
Knotenpunktes angepasst. Adapted node.
Es wird vorgeschlagen, den Schichtbaubau von außen nach innen unter Einbeziehung der vorgenannten Bauteile derart zu gestalten, dass auf die Außenschale der benachbarten Rumpfsektion innenseitig ein Spaltabdichtungsband aufgebracht ist, worauf der T-förmige Profilabschnitt des Spantprofils spaltüberbrückend aufgebracht ist, worauf die Endbereiche der beiden Stringerkupplungsteile innerhalb bzw. außerhalb des Druckbereichs aufgebracht sind. Die Befestigung erfolgt wiederum vorzugsweise durch Nieten. It is proposed to make the Schichtbaubau from outside to inside with the inclusion of the aforementioned components such that on the outer shell of the adjacent fuselage section inside a Spaltabdichtungsband is applied, whereupon the T-shaped profile section of Spantprofils is applied gap bridging, whereupon the end portions of the two Stringerkupplungsteile are applied inside or outside the printing area. The attachment is again preferably by riveting.
Um einen Spaltausgleich vorzunehmen, ist es ratsam an sich bekanntes sogenanntes Shim- Material zu verwenden, welches sich im Zusammenhang mit dem erfindungsgemäß ausgebildeten Spantprofil besonders einfach in den Spalt zwischen den benachbarten Rumpfsektion einbringen lässt. KURZE BESCHREIBUNG DER ZEICHNUNGEN To make a gap compensation, it is advisable to use known so-called shim material, which can be particularly easily introduced into the gap between the adjacent fuselage section in connection with the inventive trained Spantprofil. BRIEF DESCRIPTION OF THE DRAWINGS
Weitere, die Erfindung verbessernde Maßnahmen werden nachstehend gemeinsam mit der Beschreibung eines bevorzugten Ausführungsbeispiels der Erfindung anhand der Figuren näher dargestellt. Es zeigt: Further, measures improving the invention will be described in more detail below together with the description of a preferred embodiment of the invention with reference to FIGS. It shows:
Fig.1 eine schematische Seitenansicht eines Flugzeugs mit Druckrumpf, der aus mehreren Rumpfsektionen ohne Schalenteilung aufgebaut ist, 1 is a schematic side view of an aircraft with pressure hull, which is composed of several fuselage sections without shell division,
Fig.2 eine schematische Seitenansicht eines Flugzeugs mit Druckrumpf, der aus mehreren Rumpfsektionen mit Schalenteilung aufgebaut ist, 2 is a schematic side view of an aircraft with pressure hull, which is composed of several fuselage sections with shell division,
Fig.3 eine schematische Seitenansicht des Flugzeugrumpfs im Bereich der Druckkalotte, und A schematic side view of the fuselage in the region of the pressure calotte, and
Fig.4 eine schematische Teilvergrößerung im Bereich der Verbindungsstelle zwischen Druckkalotte und angrenzender Rumpfsektionen aus Fig.3. 4 shows a schematic partial enlargement in the region of the connection point between the pressure cap and adjacent fuselage sections from FIG.
DETAILLIERTE BESCHREIBUBNG BEISPIELHAFTER AUSFÜHRUNGSFORMEN DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS
Gemäß Figur 1 besteht der Druckrumpf des Flugzeuges in Längsrichtung gesehen aus mehreren Rumpfsektionen la-le, welche an den Grenzstellen über geschlossene ovale Ringquerschnitte miteinander verbunden sind, um einen langbauenden Druckrumpf zu fertigen. Zwischen der den Heckbereich bildenden Rumpfsektion lf und der benachbarten Rumpfsektion le ist über ein spezielles Spantprofil 5 eine heckseitige Druckkalotte 2 befestigt, welche einen flugzeuginneren Druckbereich 3 von einem nicht bedruckten According to Figure 1, the pressure hull of the aircraft seen in the longitudinal direction of several fuselage sections la-le, which are connected at the boundary points over closed oval ring cross-sections with each other to produce a long-building pressure hull. Between the fuselage section lf forming the rear region and the adjacent fuselage section le, a rear-side pressure calotte 2 is provided via a special frame profile 5 attached, which has an aircraft-internal printing area 3 of a non-printed
Heckbereich trennt, die der Rumpfsektion lf zugeordnet ist. Innerhalb des flugzeuginternen Druckbereichs 3 befinden sich die Passagierkabine sowie ein unterhalb derselben Rear section separates, which is assigned to the fuselage section lf. Within the aircraft-internal pressure range 3 are the passenger cabin and one below it
angeordneter Frachtraum. arranged cargo space.
Die Figur 2 veranschaulicht dagegen schematisch einen Druckrumpf, der nach dem so genannten Schalenteilungskonzept aufgebaut ist. Neben der herkömmlichen Rumpfsektion la, die den Bugbereich bildet, und der Rumpfsektion lf, die den Heckbereich bildet, ist die den flugzeuginneren Druckbereich 3 umgebende Außenschale des Druckrumpfs zweiteilig ausgebildet. Insoweit besteht dieser Bereich aus einer oberen Halbschale 4a und einer unteren Halbschale 4b. Beide Halbschalen 4a und 4b enden heckseitig an der Druckkalotte 2, so dass seitens des flugzeuginneren Druckbereichs 3 die beiden Halbschalen 4a und 4b an den die Druckkalotte 2 gegenüber dem Druckrumpf befestigenden Spantprofil 5 ' angrenzen. On the other hand, FIG. 2 schematically illustrates a pressure hull which is constructed according to the so-called shell division concept. In addition to the conventional fuselage section la, which forms the bow region, and the fuselage section lf, which forms the rear region, the outer shell of the pressure hull surrounding the aircraft interior pressure region 3 is formed in two parts. In that regard, this area consists of an upper half-shell 4a and a lower half-shell 4b. Both half-shells 4a and 4b terminate at the rear on the pressure cap 2, so that the two half-shells 4a and 4b adjoin the bulkhead 2, which secures the pressure cap 2 relative to the pressure hull, on the part of the airplane-internal pressure area 3.
Nach Figur 3 ist in Abstimmung mit der gewölbt scheibenartigen Formgebung der After Figure 3 is in coordination with the domed disc-like shape of the
Druckkalotte 2 das Spantprofil 5 ringförmig ausgebildet und dient neben der Befestigung der Druckkalotte 2 auch der mechanischen Verbindung der unter Atmosphärendruck stehenden Rumpfsektion le gegenüber der unbedruckten heckseitigen Rumpfsektion lf. Druckkalotte 2, the rib profile 5 annular and is used in addition to the attachment of the pressure cap 2 and the mechanical connection of the atmospheric pressure fuselage section le compared to the unprinted rear fuselage section lf.
Nach Figur 4 weist das spezielle Spantprofil 5 druckkalottenseitig einen U- förmigen According to Figure 4, the special Spantprofil 5 Druckkalottenseitig a U-shaped
Profilabschnitt auf, dessen endseitig erster Schenkel 6 über als Niete ausgebildete Profile section on whose end the first leg 6 formed as a rivet
Verbindungsmittel 7 rückwärtig an der Druckkalotte 2 befestigt ist. Demgegenüber stellt der verlängerte sich nach radial außen hin erstreckende zweite Schenkel 7 des U-förmigen Profilabschnitts eine Verbindung zu den beiden Rumpfsektionen le und lf her. Hierzu mündet der verlängerte sich nach radial außen erstreckende zweite Schenkel 8 des Connecting means 7 is secured rearwardly on the pressure cap 2. In contrast, the extended radially outwardly extending second leg 7 of the U-shaped profile section connects to the two fuselage sections le and lf. For this purpose, the extended radially outwardly extending second leg 8 of the opens
Spantprofils 5 in einen T-förmigen Profilabschnitt. Dessen Querstück 9 ist für die Frame profile 5 in a T-shaped profile section. Its cross piece 9 is for the
überbrückende Befestigung der benachbarten Rumpfsektion le und lf vorgesehen, und zwar ebenfalls durch - hier nicht weiter dargestellte - Niete. Zur Erzielung einer hinreichenden Stabilität der durch das Spantprofil 5 gebildeten bridging attachment of the adjacent fuselage section le and lf provided, also by - not shown here - rivet. To achieve a sufficient stability of the formed by the rib profile 5
Verbindungsstelle sind in Ergänzung hierzu mehrere beabstandet zueinander entlang des Umfangskreises der Druckkalotte 5 angeordnete Zugstreben 10 vorgesehen. Auch die einzelnen Zugstreben 10 sind mit dem einen Ende über die Verbindungsmittel 7 an der Druckkalotte 2 befestigt und analog mit dem anderen Ende auch an der zugeordneten druckbereichsseitigen Rumpfsektion le. Junction are provided in addition to this several spaced apart along the circumferential circle of the pressure cap 5 arranged tie rods 10. Also, the individual tie rods 10 are attached to the one end via the connecting means 7 on the pressure cap 2 and analogous to the other end also on the associated pressure range side fuselage section le.
Längsverlaufende Stringer 11 bilden beidseitig des Spantprofils 5 angeordnete Longitudinal stringer 11 form on both sides of the bulkhead profile 5 arranged
Stringerkupp lungsteile 12a und 12b einen statischen Knotenpunkt. Stringerkupp treatment parts 12a and 12b a static node.
Der Schichtaufbau im Bereich des Knotenpunktes ergibt sich von außen nach innen dergestalt, dass auf die Außenschale 13 der benachbarten Rumpfsektion le und lf innenseitig ein Spaltabdichtungsband 14 aufgebracht ist, worauf das Querstück 9 des T-förmigen The layer structure in the region of the node results from the outside to the inside in such a way that on the outer shell 13 of the adjacent fuselage section le and lf inside a Spaltabdichtungsband 14 is applied, whereupon the cross piece 9 of the T-shaped
Profilabschnitts des Spantprofils 5 spaltüberbrückend aufgebracht ist. Hier liegen die beiden Stringerkupp lungsteile 12a und 12b als eine Art Spannbacken auf. Alle vorgenannten Bauteile werden durch - nicht dargestellte - Nieten miteinander fest verbunden. Profile section of the rib profile 5 is applied gap bridging. Here are the two Stringerkupp treatment parts 12a and 12b as a kind of clamping jaws. All the above components are firmly connected by - not shown - rivets.
Ergänzend ist darauf hinzuweisen, dass„umfassend" keine anderen Elemente oder Schritte ausschließt und„eine" oder„ein" keine Vielzahl ausschließt. Ferner sei darauf hingewiesen, dass Merkmale oder Schritte, die mit Verweis auf eines der obigen Ausführungsbeispiele beschrieben worden sind, auch in Kombination mit anderen Merkmalen oder Schritten anderer oben beschriebener Ausführungsbeispiele verwendet werden können. Bezugszeichen in den Ansprüchen sind nicht als Einschränkung anzusehen. Bezugszeichen In addition, it should be understood that "comprising" does not exclude other elements or steps and "a" or "an" does not exclude a multitude. "Further, it should be noted that features or steps described with reference to one of the above embodiments also can be used in combination with other features or steps of other embodiments described above, and reference signs in the claims are not intended to be limiting. reference numeral
Rumpfsektion fuselage section
Druckkalotte  pressure bulkhead
Druckbereich  pressure range
Schalenhälfte  shell half
Spantprofil  rib profile
erster Schenkel first leg
Verbindungsmittel  connecting means
zweiter Schenkel second leg
Querstück  crosspiece
Zugstrebe  tension strut
Stringer  Stringer
Stringerkupp lungsteil  Stringerkupp ment part
Außenschale  outer shell
Spaltabdichtungsband  Gap sealing tape

Claims

A n s p r ü c h e Claims
1. Druckrumpf eines Flugzeuges, welcher in Längsrichtung aus mehreren Rumpfsektionen (la-lf) zusammengesetzt ist, wobei mindestens eine heckseitige Druckkalotte (2) zur Bildung eines flugzeuginneren Druckbereichs (3) vorgesehen ist, zu deren außenradialer Befestigung an mindestens einer Rumpfsektion (la-lf) ein ringförmiges Spantprofil (5) vorgesehen ist, 1. Pressure hull of an aircraft, which is composed in the longitudinal direction of a plurality of fuselage sections (la-lf), wherein at least one rear-side pressure calotte (2) is provided for forming an aircraft inner pressure region (3), to the outer radial attachment to at least one fuselage section (la- lf) an annular frame profile (5) is provided,
dadurch gekennzeichnet, dass das Spantprofil (5) druckkalottenseitig einen U- förmigen Profilabschnitt aufweist, dessen endseitig erster Schenkel (6) über Verbindungsmittel (7) rückwärtig an der Druckkalotte (2) befestigt ist und dessen verlängerter sich nach characterized in that the bulkhead profile (5) druckkalottenseitig has a U-shaped profile section, the end side of the first leg (6) via connecting means (7) is attached to the back of the Druckkalotte (2) and its extended after
Radialaußen erstreckender zweiter Schenkel (8) derart eine Verbindung zur mindestens einen Rumpfsektion (le, lf) herstellt, dass die Verbindungsmittel (7) allein vom flugzeuginneren Druckbereich her montierbar sind. Radially outwardly extending second leg (8) such a connection to at least one fuselage section (le, lf) establishes that the connecting means (7) are mountable solely from the aircraft interior pressure range ago.
2. Druckrumpf nach Anspruch 1, 2. Pressure hull according to claim 1,
dadurch gekennzeichnet, dass mehrere beabstandet zueinander entlang des Umfangskreises der Druckkalotte (5) angeordnete Zugstreben (10) vorgesehen sind, die mit dem einen Ende über die Verbindungsmittel (7) an der Druckkalotte (2) sowie dem Spantprofil (5) angebracht sind, und die mit dem anderen Ende an der benachbarten druckbereichsseitigen Rumpfsektion (le) angebracht sind. characterized in that a plurality of spaced apart along the peripheral circle of the pressure cap (5) arranged tie rods (10) are provided, which are attached to one end via the connecting means (7) on the pressure cap (2) and the Spantprofil (5), and which are attached to the other end to the adjacent pressure-area side fuselage section (le).
3. Druckrumpf nach Anspruch 1 , 3. Pressure hull according to claim 1,
dadurch gekennzeichnet, dass jede Zugstrebe (10) als ein hinreichend zugfestes Metallband ausgebildet ist, welches an beiden Endbereichen mit Durchbrüchen zur Aufnahme von Verbindungsmitteln (7) versehen ist. characterized in that each tension strut (10) is designed as a sufficiently tensile metal strip, which is provided at both end regions with openings for receiving connecting means (7).
4. Druckrumpf nach Anspruch 1, 4. Pressure hull according to claim 1,
dadurch gekennzeichnet, dass der verlängerte sich nach Radialaußen erstreckende zweite Schenkel (8) des Spantprofils (5) in einen T-förmigen Profilabschnitt mündet, über dessen Querstück (9) die Befestigung an der mindestens einen Rumpfsektion (le, lf) erfolgt. characterized in that the extended radially outwardly extending second leg (8) of the rib profile (5) opens into a T-shaped profile section, via whose crosspiece (9) the attachment to the at least one fuselage section (le, lf) takes place.
LK:hv LK: hv
5. Druckrum f nach Anspruch 4, 5. Druckrum f according to claim 4,
dadurch gekennzeichnet, dass das Querstück (9) des T-förmigen Profilabschnitts zwei benachbarte Rumpfsektionen miteinander verbindet. characterized in that the crosspiece (9) of the T-shaped profile section connects two adjacent fuselage sections with each other.
6. Druckrumpf nach Anspruch 4, 6. Pressure hull according to claim 4,
dadurch gekennzeichnet, dass zur Befestigung der mindestens einen Rumpfsektion (le; lf) am Querstück (9) des Spantprofils (5) ebenfalls Nieten als Verbindungsmittel vorgesehen sind. characterized in that for fastening the at least one fuselage section (le; lf) on the crosspiece (9) of the bulkhead profile (5) also rivets are provided as connecting means.
7. Druckrumpf nach Anspruch 1, 7. Pressure hull according to claim 1,
dadurch gekennzeichnet, dass die Rumpfkonstruktion im Druckbereich (3) längsgeteilte Schalenhälften (4a, 4b) umfassen. characterized in that the hull construction in the pressure region (3) comprises longitudinally split shell halves (4a, 4b).
8. Druckrump f nach Anspruch 7 , 8. Druckrump f according to claim 7,
dadurch gekennzeichnet, dass das Spantprofil (5') in Anpassung an die Schalenhälften (4a, 4b) zweiteilig ausgeführt ist, wobei jedes Spantprofilteil ein Ringsegment von 180° bildet. characterized in that the bulkhead profile (5 ') in adaptation to the shell halves (4a, 4b) is made in two parts, each Spantprofilteil forms a ring segment of 180 °.
9. Druckrumpf nach Anspruch 1, 9. Pressure hull according to claim 1,
dadurch gekennzeichnet, dass das Spantprofil (5) in Anpassung an einen gewickelten Rumpf einteilig ausgeführt ist und somit einen vollen Ring von 360° bildet. characterized in that the frame profile (5) is made in one piece in adaptation to a wound hull and thus forms a full ring of 360 °.
10. Druckrumpf nach Anspruch 1, 10. Pressure hull according to claim 1,
dadurch gekennzeichnet, dass das aus U- förmigem und T-förmigem Profilabschnitt zusammengesetzte Spantprofil (5a: 5') als ein aus einem Leichtmetall bestehendes Fräsbauteil gefertigt ist. characterized in that the composite of U-shaped and T-shaped profile section Spantprofil (5 a: 5 ') is made as a light alloy existing milling component.
11. Druckrum f nach Anspruch 1 , 11. Druckrum f according to claim 1,
dadurch gekennzeichnet, dass längsverlaufende Stringer (11) über beidseitig des characterized in that longitudinal stringers (11) over both sides of the
Spantprofils (5) angeordnete Stringerkupp lungsteile (12a, 12b) einen statischen Knotenpunkt bilden. Spantprofils (5) arranged Stringerkupp treatment parts (12a, 12b) form a static node.
12. Druckrumpf nach Anspruch 11 , 12. Pressure hull according to claim 11,
dadurch gekennzeichnet, dass auf die Außenschale (13) der benachbarten Rumpfsektion (le, lf) innenseitig ein Spaltabdichtungsband (14) aufgebracht ist, worauf der T-förmige characterized in that on the outer shell (13) of the adjacent fuselage section (le, lf) inside a Spaltabdichtungsband (14) is applied, whereupon the T-shaped
Profilabschnitt des Spantprofils (5) spaltüberbrückend aufgebracht ist, worauf die Profile section of the Spantprofils (5) is applied gap bridging, whereupon the
Endbereiche der beiden Stringerkupp lungsteile (12a, 12b) innerhalb bzw. außerhalb des Druckbereichs (3) aufgebracht sind. End portions of the two Stringerkupp treatment parts (12 a, 12 b) within or outside the printing area (3) are applied.
EP10762689.7A 2009-10-09 2010-10-07 Pressure fuselage of an aircraft comprising a tail-face pressure calotte Not-in-force EP2485941B1 (en)

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DE102009049007A DE102009049007A1 (en) 2009-10-09 2009-10-09 Pressure hull of an airplane with rear-side pressure calotte
PCT/EP2010/065037 WO2011042511A2 (en) 2009-10-09 2010-10-07 Pressure fuselage of an aircraft comprising a tail-face pressure calotte

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DE102009049007A1 (en) 2011-04-21
CN102574571A (en) 2012-07-11
CA2776027A1 (en) 2011-04-14
CN102574571B (en) 2015-09-09
WO2011042511A3 (en) 2011-07-21
RU2493049C1 (en) 2013-09-20
US8939404B2 (en) 2015-01-27
EP2485941B1 (en) 2015-08-05
WO2011042511A2 (en) 2011-04-14
US20120228427A1 (en) 2012-09-13

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